Satellite-based laser communication connection method and device, electronic equipment and medium

Abstract

The application provides a satellite-based laser communication connection method and device, electronic equipment and medium, and relates to the technical field of satellite communication. The satellite-based laser communication connection method comprises the following steps: in the case that the laser communication interruption information of a target satellite is acquired, the coarse alignment judgment information corresponding to the target satellite is called, and the target scanning range corresponding to the target satellite is determined based on the coarse alignment judgment information; the historical ephemeris information corresponding to the target satellite in a preset number of historical unit time periods is acquired, and the multiple simulated relative position relationships of the target satellite are determined according to the multiple historical ephemeris information; the scanning mode corresponding to the target scanning range is determined by using the multiple simulated relative position relationships, and the laser scanning confirmation and interruption connection of the target satellite are completed based on the scanning mode. The application can improve the real-time performance and reliability of the laser communication link establishment.

Description

Technical Field

[0001] This application relates to the field of satellite communication technology, and in particular to a satellite-based laser communication connection method, device, electronic device, and medium. Background Technology

[0002] With the rapid development of satellite communication technology, laser communication has become an important means of data transmission between satellites due to its advantages such as high bandwidth, low latency, and strong anti-interference capabilities. However, under the influence of high-speed satellite motion and complex space environment, laser communication links are prone to interruption due to attitude disturbances, orbital deviations, or interference from obstructions. Therefore, rapid and accurate laser communication reconnection is required. Traditional reconnection methods involve coarse alignment followed by omnidirectional scanning within a specific range to determine the precise position of the target satellite and establish a laser communication connection.

[0003] However, the applicant of this application found that in traditional reconnection methods, the scanning method for scanning a specific range is relatively simple, often using a fixed step size for full-area scanning, and the positional changes of the target satellite are not considered during the scanning process. This results in a long scanning time and low scanning efficiency for a specific scanning method, which is difficult to meet the real-time requirements of satellite communication for rapid reconnection. Summary of the Invention

[0004] To improve the real-time performance and reliability of laser communication link establishment, this application provides a satellite-based laser communication connection method, device, electronic device, and medium.

[0005] This application provides a satellite-based laser communication connection method, which adopts the following technical solution: A satellite-based laser communication connection method includes: upon receiving laser communication interruption information of a target satellite, retrieving coarse alignment assessment information corresponding to the target satellite, and determining the target scanning range corresponding to the target satellite based on the coarse alignment assessment information; acquiring historical ephemeris information corresponding to a preset number of historical unit time periods for the target satellite, and determining multiple simulated relative positional relationships of the target satellite based on the multiple historical ephemeris information; using the multiple simulated relative positional relationships to determine the scanning mode corresponding to the target scanning range, and completing laser scanning confirmation and interruption connection establishment of the target satellite based on the scanning mode, wherein the scanning mode is a mode for scanning the target scanning range based on a determined specific scanning rule.

[0006] According to some embodiments, the above-mentioned process of retrieving coarse alignment assessment information corresponding to the target satellite when laser communication interruption information of the target satellite is obtained includes: generating a satellite laser coarse alignment command when laser communication interruption information is obtained, and obtaining the first ephemeris information of the target satellite at the time of communication interruption and the second ephemeris information of the laser emitting satellite corresponding to the target satellite based on the satellite laser coarse alignment command; substituting the first ephemeris information and the second ephemeris information into a preset coarse alignment model to perform coarse alignment assessment, thereby obtaining coarse alignment assessment information corresponding to the target satellite.

[0007] According to some embodiments, the above-mentioned determination of the target scanning range corresponding to the target satellite based on coarse alignment assessment information includes: determining the residual error information and center point information corresponding to the target satellite based on coarse alignment assessment information; determining the scanning radius corresponding to the target satellite based on the residual error information; and constructing the target scanning range corresponding to the target satellite based on the scanning radius and center point information.

[0008] According to some embodiments, the aforementioned multiple historical ephemeris information are all information from the set of the first historical ephemeris information of the target satellite and the second historical ephemeris information of the laser emitting satellite corresponding to the target satellite. Based on the multiple historical ephemeris information, determining multiple simulated relative positional relationships of the target satellite includes: retrieving a preset coarse alignment model and substituting the corresponding first and second historical ephemeris information into the preset coarse alignment model to determine multiple simulated scanning ranges corresponding to the target satellite; obtaining the target position information of the target satellite corresponding to the multiple historical ephemeris information respectively; and determining multiple simulated relative positional relationships of the target satellite based on the multiple simulated scanning ranges and the multiple target position information.

[0009] According to some embodiments, the above-mentioned method of determining the scanning mode corresponding to the target scanning range by utilizing multiple simulated relative positional relationships includes: determining multiple virtual two-dimensional planes corresponding to the target satellite based on multiple simulated relative positional relationships; overlapping the multiple virtual two-dimensional planes according to time sequence to obtain a target virtual two-dimensional plane, wherein the target virtual two-dimensional plane contains multiple target position information corresponding to the target satellite; determining position change information corresponding to the multiple target position information; and determining the scanning mode corresponding to the target scanning range based on the position change information.

[0010] According to some embodiments, the above-mentioned method of determining the scanning mode corresponding to the target scanning range based on position change information includes: dividing the target scanning range into regions based on a preset range division rule to obtain multiple sub-target scanning ranges; determining the hit probability corresponding to the multiple sub-target scanning ranges based on position change information; determining the scanning order corresponding to the multiple target scanning ranges based on the hit probability; and determining the scanning mode corresponding to the target scanning range based on the scanning order.

[0011] According to some embodiments, the above-mentioned method of dividing the target scanning range into regions based on preset range division rules to obtain multiple sub-target scanning ranges includes: dividing the target scanning range into an initial target scanning range based on multiple preset range division rules included in the preset range division rules, wherein the initial target scanning range includes a circular region and multiple annular regions; and dividing the initial target scanning range into multiple sub-target scanning ranges based on preset angle thresholds included in the preset range division rules.

[0012] This application provides a satellite-based laser communication connection device, which adopts the following technical solution: A satellite-based laser communication connection device includes: a target scanning range determination module, a relative position relationship determination module, and a laser communication reconnection module. The target scanning range determination module is used to retrieve coarse alignment assessment information corresponding to the target satellite when laser communication interruption information of the target satellite is obtained, and to determine the target scanning range corresponding to the target satellite based on the coarse alignment assessment information. The relative position relationship determination module is used to obtain historical ephemeris information corresponding to the target satellite within a preset number of historical unit time periods, and to determine multiple simulated relative position relationships of the target satellite based on the multiple historical ephemeris information. The laser communication reconnection module is used to determine the scanning mode corresponding to the target scanning range using the multiple simulated relative position relationships, and to complete laser scanning confirmation and interruption reconnection of the target satellite based on the scanning mode. The scanning mode is a mode for scanning the target scanning range based on a determined specific scanning rule.

[0013] According to some embodiments, the target scanning range determination module described above is specifically used to: generate a satellite laser coarse alignment command when laser communication interruption information is obtained, and based on the satellite laser coarse alignment command, obtain the first ephemeris information of the target satellite at the time of communication interruption and the second ephemeris information of the laser emitting satellite corresponding to the target satellite; substitute the first ephemeris information and the second ephemeris information into a preset coarse alignment model to perform coarse alignment judgment, thereby obtaining coarse alignment judgment information corresponding to the target satellite.

[0014] According to some embodiments, the target scanning range determination module described above is specifically used for: determining the residual error information and center point information corresponding to the target satellite based on coarse alignment assessment information; determining the scanning radius corresponding to the target satellite based on the residual error information; and constructing the target scanning range corresponding to the target satellite based on the scanning radius and center point information.

[0015] According to some embodiments, the aforementioned multiple historical ephemeris information are all information from the set of the first historical ephemeris information of the target satellite and the second historical ephemeris information of the laser emitting satellite corresponding to the target satellite. The aforementioned relative position relationship determination module is specifically used to: retrieve a preset coarse alignment model, and substitute the first historical ephemeris information and the second historical ephemeris information that have a corresponding relationship into the preset coarse alignment model to determine multiple simulated scanning ranges corresponding to the target satellite; obtain the target position information of the target satellite corresponding to the multiple historical ephemeris information respectively; and determine multiple simulated relative position relationships corresponding to the target satellite based on the multiple simulated scanning ranges and the multiple target position information.

[0016] According to some embodiments, the laser communication reconnection module described above is specifically used for: determining multiple virtual two-dimensional planes corresponding to the target satellite based on multiple simulated relative positional relationships; overlapping the multiple virtual two-dimensional planes according to time sequence to obtain a target virtual two-dimensional plane, wherein the target virtual two-dimensional plane contains multiple target position information corresponding to the target satellite; determining position change information corresponding to the multiple target position information; and determining the scanning mode corresponding to the target scanning range based on the position change information.

[0017] According to some embodiments, the laser communication reconnection module described above is specifically used for: dividing the target scanning range into regions based on a preset range division rule to obtain multiple sub-target scanning ranges; determining the hit probability corresponding to the multiple sub-target scanning ranges based on position change information; determining the scanning order corresponding to the multiple target scanning ranges based on the hit probability; and determining the scanning mode corresponding to the target scanning range based on the scanning order.

[0018] According to some embodiments, the laser communication reconnection module described above is specifically used to: divide the target scanning range based on multiple preset range division rules included in the preset range division rules to obtain an initial target scanning range, wherein the initial target scanning range includes a circular region and multiple annular regions; and divide the initial target scanning range based on preset angle thresholds included in the preset range division rules to obtain multiple sub-target scanning ranges.

[0019] This application provides an electronic device that adopts the following technical solution: An electronic device comprising: processor; The memory stores a computer program, which, when executed by the processor, causes the processor to perform the aforementioned satellite-based laser communication connection method.

[0020] This application provides a computer-readable medium, which adopts the following technical solution: A computer-readable medium having a computer program stored thereon, which, when executed by a processor, causes the processor to perform the aforementioned satellite-based laser communication connection method.

[0021] According to the embodiments provided in this application, when laser communication interruption information of the target satellite is obtained, coarse alignment judgment information obtained through a pre-set coarse alignment judgment strategy is retrieved, and the target scanning range required for reconnection of the target satellite during the interruption is obtained based on the coarse alignment judgment information. Subsequently, the electronic device determines multiple simulated relative positional relationships of the target satellite in different historical unit time periods before the interruption by simulating coarse alignment judgment methods, and generates multiple virtual two-dimensional planes corresponding to the target satellite based on the multiple simulated relative positional relationships. By overlapping the multiple virtual two-dimensional planes based on the time sequence and the positional changes of the target satellite, the scanning mode adapted to the target scanning range is determined, and the scanning confirmation and interruption reconnection of the target satellite are completed based on the scanning mode, thereby realizing the rapid recovery of the laser communication link, effectively shortening the time for interruption reconnection, and improving the accuracy and efficiency of the scanning process. Attached Figure Description

[0022] Figure 1 This is a block diagram illustrating a satellite-based laser communication connection method according to an embodiment of this application; Figure 2 This is a block diagram of a satellite-based laser communication connection device according to an embodiment of this application; Figure 3 This is a schematic diagram of an electronic device according to an embodiment of this application.

[0023] Explanation of reference numerals in the attached figures: 20: Satellite-based laser communication connection device; 201: Target scanning range determination module; 202: Relative position relationship determination module; 203: Laser communication reconnection module; 30: Electronic device; 301: Processor; 302: Bus; 303: Memory; 304: Transceiver. Detailed Implementation

[0024] The following is in conjunction with the appendix Figures 1-3 This application will be described in further detail.

[0025] To make the objectives, technical solutions, and advantages of the embodiments of this application clearer, the technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this application, not all embodiments. Based on the embodiments of this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0026] This application provides a satellite-based laser communication connection method, which can be executed by an electronic device. The electronic device can be a server, which can be an independent physical server, a server cluster composed of multiple physical servers, or a distributed device, or a cloud server that provides cloud computing services. The server can be installed on a ground terminal or on a high-orbit satellite.

[0027] Reference Figure 1 A satellite-based laser communication connection method includes steps S101, S102, S103, and S104, wherein... S101, upon obtaining laser communication interruption information of the target satellite, retrieve the coarse alignment assessment information corresponding to the target satellite, and determine the target scanning range corresponding to the target satellite based on the coarse alignment assessment information.

[0028] In some embodiments, the target satellite is the satellite that receives laser communication data during laser communication, such as a low-Earth orbit satellite or a medium-Earth orbit satellite; laser communication interruption information refers to the information generated when the laser link of the target satellite is interrupted due to pointing deviation, atmospheric turbulence, obstructions or other interference factors during laser communication; coarse alignment judgment information is relevant information used to determine the approximate pointing range of the target satellite by calculation through a pre-set coarse alignment strategy; target scanning range refers to the angle or spatial range used to perform a preliminary scan of the target satellite based on the coarse alignment judgment information.

[0029] The electronic equipment monitors the laser communication link status between the target satellite and its corresponding laser emitting satellite in real time. If the monitoring process detects that the laser communication between the target satellite and its corresponding laser emitting satellite has been interrupted, it indicates that the laser communication link between the target satellite and its corresponding laser emitting satellite has been interrupted. At this time, it is necessary to re-establish the laser communication link between the target satellite and its corresponding laser emitting satellite. First, the electronic equipment retrieves the coarse alignment judgment information corresponding to the target satellite and analyzes the coarse alignment judgment information to determine the approximate pointing range of the target satellite at the current moment, that is, the target scanning range.

[0030] S102, acquire the historical ephemeris information of the target satellite within a preset number of historical unit time periods, and determine multiple simulated relative positional relationships of the target satellite based on the multiple historical ephemeris information.

[0031] In some embodiments, historical ephemeris information is a collection of information such as the orbital position, velocity vector, and timestamp of the target satellite and its corresponding laser emitting satellite within a preset number of historical unit time periods. The historical unit time period can be several seconds, minutes, or orbital cycles in the past, and is continuous in time. The specific value of the historical unit time period can be set according to actual needs. The simulated relative positional relationship is the positional relationship between the target position of the target satellite and the simulated scanning range obtained by simulating calculations using a pre-set coarse alignment strategy when the target satellite and its corresponding laser emitting satellite are in normal laser communication within the historical unit time period.

[0032] The electronic device generates an information acquisition command and sends it to the target satellite and its corresponding laser emitting satellite. The target satellite and the laser emitting satellite respond to the information acquisition command and send their respective historical ephemeris information within a preset number of historical unit time periods to the electronic device. Subsequently, the electronic device calls a pre-set coarse alignment strategy to simulate the simulated relative positional relationship between the target satellite and the laser emitting satellite when maintaining normal laser communication within the historical unit time period.

[0033] S103 uses multiple simulated relative positional relationships to determine the scanning mode corresponding to the target scanning range, and based on the scanning mode, completes the laser scanning confirmation of the target satellite and interrupts the connection establishment.

[0034] In some embodiments, the scanning mode is a mode that scans the target scanning range based on a determined specific scanning rule.

[0035] The electronic equipment performs spatial mapping and analysis on multiple simulated relative positional relationships, and divides the target scanning range into multiple sub-target scanning areas. Subsequently, based on the results of the spatial mapping and analysis, the electronic equipment determines the probability distribution of the target satellite's position within each sub-target scanning area, and generates a scanning pattern accordingly, prioritizing the scanning of sub-target scanning areas with higher probabilities, thereby improving scanning efficiency and connection establishment success rate. Simultaneously, the electronic equipment generates corresponding scanning control commands based on the scanning pattern and sends these commands to the laser transmitting satellite, enabling it to perform laser scanning confirmation and interrupt connection establishment of the target satellite according to the determined scanning pattern. This effectively shortens the scanning time while ensuring scanning accuracy, improving the real-time performance and reliability of laser communication link establishment.

[0036] In step S101, when the laser communication interruption information of the target satellite is obtained, the coarse alignment assessment information corresponding to the target satellite is retrieved, including: when the laser communication interruption information is obtained, generating a satellite laser coarse alignment command, and based on the satellite laser coarse alignment command, obtaining the first ephemeris information of the target satellite at the time of communication interruption and the second ephemeris information of the laser emitting satellite corresponding to the target satellite; substituting the first ephemeris information and the second ephemeris information into a preset coarse alignment model to perform coarse alignment assessment, thereby obtaining the coarse alignment assessment information corresponding to the target satellite.

[0037] In some embodiments, upon receiving laser communication interruption information, the electronic device immediately initiates an interruption response process. This involves the electronic device generating a coarse alignment command for the satellite laser. This command includes a timestamp of the interruption time and identification information for both the target satellite and the laser-emitting satellite. Subsequently, based on this command, the electronic device retrieves the first ephemeris information corresponding to the target satellite and the second ephemeris information corresponding to its corresponding laser-emitting satellite from the ephemeris database at the time of the communication interruption. These two sets of ephemeris information are then input into a preset coarse alignment model for coarse alignment assessment. This model, based on satellite orbital dynamics and relative motion equations, calculates the approximate pointing angle and distance deviation between the two satellites at the time of the interruption, thereby generating coarse alignment assessment information including azimuth, elevation, and distance offset.

[0038] In some embodiments, the preset coarse alignment model is constructed based on satellite orbital dynamics and relative motion equations. It can quickly calculate the relative position and attitude deviation between the two satellites at the moment of interruption based on the two sets of input ephemeris information, thereby generating coarse alignment judgment information including azimuth angle, pitch angle and distance offset.

[0039] In step S101, the target scanning range corresponding to the target satellite is determined based on the coarse alignment assessment information, including: determining the residual error information and center point information corresponding to the target satellite based on the coarse alignment assessment information; determining the scanning radius corresponding to the target satellite based on the residual error information; and constructing the target scanning range corresponding to the target satellite based on the scanning radius and center point information.

[0040] In some embodiments, the residual error information is the pointing deviation margin caused by factors such as the accuracy limitations of the coarse alignment model itself and the timeliness of ephemeris data; the center point information is the theoretical pointing position calculated by the coarse alignment model.

[0041] After acquiring the coarse alignment assessment information, the electronic equipment first extracts the azimuth, elevation, and range offset to determine the residual error information after coarse alignment. This residual error information includes angular residual error and range residual error, reflecting the pointing deviation caused by factors such as ephemeris accuracy and orbital perturbation during the coarse alignment process. Subsequently, based on the angular residual error in the residual error information and a preset error amplification factor, the electronic equipment calculates the scanning radius. The formula for calculating the scanning radius is: Scanning radius = Angular residual error × Error amplification factor. The error amplification factor is dynamically adjusted according to the historical communication link quality to ensure that the scanning range covers the potential deviation area. Then, using the center point information in the coarse alignment assessment information as a reference and the scanning radius as the range, the electronic equipment constructs a circular scanning area centered on the center point, which serves as the target scanning range for the target satellite.

[0042] In some embodiments, the multiple historical ephemeris information are all information from the set of the first historical ephemeris information of the target satellite and the second historical ephemeris information of the laser emitting satellite corresponding to the target satellite. Then, in step S102, the multiple simulated relative positional relationships of the target satellite are determined based on the multiple historical ephemeris information, including: retrieving a preset coarse alignment model and substituting the first historical ephemeris information and the second historical ephemeris information that have a corresponding relationship into the preset coarse alignment model to determine multiple simulated scanning ranges corresponding to the target satellite; obtaining the target position information of the target satellite corresponding to the multiple historical ephemeris information respectively; and determining the multiple simulated relative positional relationships of the target satellite based on the multiple simulated scanning ranges and the multiple target position information.

[0043] In some embodiments, the electronic device inputs multiple historical ephemeris information, namely the first historical ephemeris information and the second historical ephemeris information, into a preset coarse alignment model; through the calculation of the preset coarse alignment model, the simulated scanning range corresponding to each historical moment is obtained; at the same time, the electronic device obtains the target position information of the target satellite corresponding to each historical moment, and compares the multiple simulated scanning ranges with the multiple target position information to determine the simulated relative position relationship of each historical moment.

[0044] In some embodiments, the electronic device compares the target location information one by one to see if it falls within the corresponding simulated scanning range. If the target location information falls within the simulated scanning range, the simulated relative positional relationship at that moment is determined to be effective coverage; otherwise, it is determined to be invalid coverage. By statistically analyzing the ratio of the number of effective coverages to the total number of historical moments, the coverage performance of the coarse alignment model can be evaluated. If the effective coverage ratio is lower than a preset threshold, a model parameter adjustment process is triggered. By optimizing the error amplification coefficient or correcting the ephemeris input deviation, the effective coverage probability of the simulated relative positional relationship at subsequent moments is improved, thereby enhancing the reliability and stability of the laser communication link establishment.

[0045] In step S103, the scanning mode corresponding to the target scanning range is determined using multiple simulated relative positional relationships, including: determining multiple virtual two-dimensional planes corresponding to the target satellite based on multiple simulated relative positional relationships; overlapping the multiple virtual two-dimensional planes according to time sequence to obtain a target virtual two-dimensional plane, wherein the target virtual two-dimensional plane contains multiple target position information corresponding to the target satellite; determining the position change information corresponding to the multiple target position information; and determining the scanning mode corresponding to the target scanning range based on the position change information.

[0046] In some embodiments, the virtual two-dimensional plane is constructed based on the position of the target satellite. The constructed virtual plane is used to characterize the projection of the simulated relative positional relationship of the target satellite at different historical moments in space.

[0047] The electronic device constructs multiple virtual two-dimensional planes using azimuth and elevation angles in a simulated relative positional relationship as coordinate axes. These virtual two-dimensional planes are then superimposed in chronological order to form a target virtual two-dimensional plane. On this target virtual two-dimensional plane, the target position information at each historical moment is presented as discrete points. These points collectively outline the target satellite's trajectory in space, providing an intuitive spatial distribution basis for determining the scanning mode. The electronic device further analyzes the distribution density and changing trends of these discrete points to identify the target satellite's movement patterns, including its velocity vector, acceleration characteristics, and periodic fluctuations, thus obtaining the position change information corresponding to each target position. Based on this position change information, the electronic device determines the optimal scanning mode.

[0048] In some embodiments, determining the scanning mode corresponding to the target scanning range based on position change information includes: dividing the target scanning range into regions based on a preset range division rule to obtain multiple sub-target scanning ranges; determining the hit probability corresponding to the multiple sub-target scanning ranges based on position change information; determining the scanning order corresponding to the multiple target scanning ranges based on the hit probability; and determining the scanning mode corresponding to the target scanning range based on the scanning order.

[0049] After receiving position change information, the electronic equipment retrieves preset range division rules and divides the target scanning range into multiple sub-target scanning ranges according to spatial orientation or time window. Subsequently, based on the position change information, the electronic equipment calculates the probability of the target satellite appearing within each sub-target scanning range, i.e., the hit probability. The higher the hit probability, the more worthy the sub-region is of priority for scanning. The electronic equipment sorts the sub-target scanning ranges from high to low according to the hit probability, determines the scanning priority of each sub-target scanning range, and generates a dynamic scanning scheduling strategy, i.e., the scanning mode, accordingly.

[0050] In some embodiments, the target scanning range is divided into regions based on preset range division rules to obtain multiple sub-target scanning ranges, including: dividing the target scanning range based on multiple preset range division rules included in the preset range division rules to obtain an initial target scanning range, wherein the initial target scanning range includes a circular region and multiple annular regions; and dividing the initial target scanning range based on preset angle thresholds included in the preset range division rules to obtain multiple sub-target scanning ranges.

[0051] In some embodiments, the electronic device invokes multiple preset range division rules included in the preset range division rules to divide the target scanning range into a circular region and multiple concentric annular regions, wherein the circular region is located at the center and the annular regions expand outward sequentially; subsequently, the electronic device retrieves preset angle thresholds included in the preset range division rules to perform angle division on each annular region, thereby further subdividing the initial target scanning range into multiple fan-shaped sub-regions, i.e., obtaining multiple sub-target scanning ranges. In this "radial layering and angle segmentation" division method, the breadth and accuracy of the scan can be taken into account, enabling the electronic device to more meticulously evaluate the probability of target occurrence in each sub-region in subsequent hit probability calculations, thereby optimizing the allocation efficiency of scanning resources.

[0052] This application provides a satellite-based laser communication connection device, which adopts the following technical solution: Reference Figure 2 A satellite-based laser communication connection device 20 includes: a target scanning range determination module 201, a relative position relationship determination module 202, and a laser communication reconnection module 203. The target scanning range determination module 201 is used to retrieve coarse alignment assessment information corresponding to the target satellite when laser communication interruption information of the target satellite is obtained, and to determine the target scanning range corresponding to the target satellite based on the coarse alignment assessment information. The relative position relationship determination module 202 is used to obtain historical ephemeris information corresponding to the target satellite within a preset number of historical unit time periods, and to determine multiple simulated relative position relationships of the target satellite based on multiple historical ephemeris information. The laser communication reconnection module 203 is used to determine the scanning mode corresponding to the target scanning range using multiple simulated relative position relationships, and to complete laser scanning confirmation and interruption reconnection of the target satellite based on the scanning mode. The scanning mode is a mode for scanning the target scanning range based on a determined specific scanning rule.

[0053] In some embodiments, the target scanning range determination module 201 described above is specifically used to: generate a satellite laser coarse alignment command when laser communication interruption information is obtained, and based on the satellite laser coarse alignment command, obtain the first ephemeris information of the target satellite at the time of communication interruption and the second ephemeris information of the laser emitting satellite corresponding to the target satellite; substitute the first ephemeris information and the second ephemeris information into a preset coarse alignment model to perform coarse alignment judgment, thereby obtaining coarse alignment judgment information corresponding to the target satellite.

[0054] In some embodiments, the target scanning range determination module 201 described above is specifically used to: determine the residual error information and center point information corresponding to the target satellite based on the coarse alignment assessment information; determine the scanning radius corresponding to the target satellite based on the residual error information; and construct the target scanning range corresponding to the target satellite based on the scanning radius and center point information.

[0055] In some embodiments, the aforementioned multiple historical ephemeris information are all information from the set of the first historical ephemeris information of the target satellite and the second historical ephemeris information of the laser emitting satellite corresponding to the target satellite. The aforementioned relative position relationship determination module 202 is specifically used to: retrieve a preset coarse alignment model, and substitute the first historical ephemeris information and the second historical ephemeris information that have a corresponding relationship into the preset coarse alignment model to determine multiple simulated scanning ranges corresponding to the target satellite; obtain the target position information of the target satellite corresponding to the multiple historical ephemeris information respectively; and determine multiple simulated relative position relationships corresponding to the target satellite based on the multiple simulated scanning ranges and the multiple target position information.

[0056] In some embodiments, the laser communication reconnection module 203 described above is specifically used for: determining multiple virtual two-dimensional planes corresponding to the target satellite based on multiple simulated relative position relationships; overlapping the multiple virtual two-dimensional planes according to time sequence to obtain a target virtual two-dimensional plane, wherein the target virtual two-dimensional plane contains multiple target position information corresponding to the target satellite; determining position change information corresponding to the multiple target position information; and determining the scanning mode corresponding to the target scanning range based on the position change information.

[0057] In some embodiments, the laser communication reconnection module 203 described above is specifically used to: divide the target scanning range into regions based on a preset range division rule to obtain multiple sub-target scanning ranges; determine the hit probability corresponding to the multiple sub-target scanning ranges based on position change information; determine the scanning order corresponding to the multiple target scanning ranges based on the hit probability, and determine the scanning mode corresponding to the target scanning range based on the scanning order.

[0058] In some embodiments, the laser communication reconnection module 203 described above is specifically used to: divide the target scanning range based on a plurality of preset range division rules included in the preset range division rules to obtain an initial target scanning range, wherein the initial target scanning range includes a circular region and a plurality of annular regions; and divide the initial target scanning range based on a preset angle threshold included in the preset range division rules to obtain a plurality of sub-target scanning ranges.

[0059] In some embodiments, the target scanning range determination module 201 may include logic circuits or be implemented by a central processing unit, digital signal processor, or field-programmable gate array (FPGA) included in an electronic device; the relative position relationship determination module 202 may include logic circuits or be implemented by a central processing unit, digital signal processor, or FPGA included in an electronic device; the laser communication reconnection module 203 may include logic circuits or be implemented by a central processing unit, digital signal processor, or FPGA included in an electronic device.

[0060] Those skilled in the art will understand that, for the sake of convenience and brevity, the specific working processes of the systems, modules, and units described above can be referred to the corresponding processes in the foregoing method embodiments, and will not be repeated here.

[0061] This application discloses an electronic device, including: a processor; and a memory storing a computer program, which, when executed by the processor, causes the processor to execute the above-described satellite-based laser communication connection method.

[0062] For example, refer to Figure 3 , Figure 3 The illustrated electronic device 30 includes a processor 301 and a memory 303. The processor 301 and the memory 303 are connected, for example, via a bus 302. Optionally, the electronic device 30 may also include a transceiver 304. It should be noted that in practical applications, the transceiver 304 is not limited to one type, and the structure of this electronic device 30 does not constitute a limitation on the embodiments of the present invention.

[0063] Processor 301 may be a CPU (Central Processing Unit), a general-purpose processor, a DSP (Digital Signal Processor), an ASIC (Application Specific Integrated Circuit), an FPGA (Field Programmable Gate Array), or other programmable logic devices, transistor logic devices, hardware components, or any combination thereof. It can implement or execute the various exemplary logic blocks, modules, and circuits described in this disclosure. Processor 301 may also be a combination that implements computational functions, such as a combination of one or more microprocessors, a combination of a DSP and a microprocessor, etc.

[0064] Bus 302 may include a pathway for transmitting information between the aforementioned components. Bus 302 may be a PCI (Peripheral Component Interconnect) bus or an EISA (Extended Industry Standard Architecture) bus, etc. Bus 302 can be divided into address bus, data bus, control bus, etc. For ease of representation, Figure 3 The bus is represented by a single thick line, but this does not mean that there is only one bus or one type of bus.

[0065] The memory 303 may be a ROM (Read Only Memory) or other type of static storage device capable of storing static information and instructions, RAM (Random Access Memory) or other type of dynamic storage device capable of storing information and instructions, or an EEPROM (Electrically Erasable Programmable Read Only Memory), CD-ROM (Compact Disc Read Only Memory) or other optical disc storage, optical disc storage (including compressed optical discs, laser discs, optical discs, digital universal optical discs, Blu-ray discs, etc.), magnetic disk media or other magnetic storage devices, or any other medium capable of carrying or storing desired program code in the form of instructions or data structures and accessible by a computer, but not limited thereto.

[0066] The memory 303 stores application code that executes the present invention and is controlled by the processor 301. The processor 301 executes the application code stored in the memory 303 to implement the content shown in the foregoing method embodiments.

[0067] Figure 3 The electronic device shown is merely an example and should not be construed as limiting the functionality and scope of the embodiments of the present invention.

[0068] This application discloses a computer-readable medium storing a computer program that, when executed by a processor, causes the processor to perform a satellite-based laser communication connection method.

[0069] It should be understood that although the steps in the flowcharts of the accompanying figures are shown sequentially as indicated by the arrows, these steps are not necessarily executed in the order indicated by the arrows. Unless explicitly stated herein, there is no strict order restriction on the execution of these steps, and they can be executed in other orders. Moreover, at least some steps in the flowcharts of the accompanying figures may include multiple sub-steps or multiple stages. These sub-steps or stages are not necessarily completed at the same time, but can be executed at different times, and their execution order is not necessarily sequential, but can be performed alternately or in turn with other steps or at least some of the sub-steps or stages of other steps.

[0070] The above are only some embodiments of this application. It should be noted that for those skilled in the art, several improvements and modifications can be made without departing from the principle of this application, and these improvements and modifications should also be considered within the scope of protection of this application.

Claims

1. A satellite-based laser communication connection method, characterized in that, include: Upon receiving information indicating that the laser communication of the target satellite has been interrupted, the coarse alignment assessment information corresponding to the target satellite is retrieved, and based on the coarse alignment assessment information, the target scanning range corresponding to the target satellite is determined. The system acquires historical ephemeris information corresponding to a preset number of historical unit time periods for the target satellite, and determines multiple simulated relative positional relationships of the target satellite based on the multiple historical ephemeris information. Using the multiple simulated relative positional relationships, the scanning mode corresponding to the target scanning range is determined, and based on the scanning mode, the laser scanning confirmation and interruption connection establishment of the target satellite are completed. The scanning mode is a mode for scanning the target scanning range based on a determined specific scanning rule.

2. The method according to claim 1, characterized in that, The step of retrieving coarse alignment assessment information corresponding to the target satellite when laser communication interruption information of the target satellite is obtained includes: Upon receiving the laser communication interruption information, a satellite laser coarse alignment command is generated, and based on the satellite laser coarse alignment command, the first ephemeris information of the target satellite at the time of the communication interruption and the second ephemeris information of the laser emitting satellite corresponding to the target satellite are obtained. The first ephemeris information and the second ephemeris information are substituted into a preset coarse alignment model for coarse alignment analysis, thereby obtaining coarse alignment analysis information corresponding to the target satellite.

3. The method according to claim 1, characterized in that, The step of determining the target scanning range corresponding to the target satellite based on the coarse alignment assessment information includes: Based on the coarse alignment assessment information, the residual error information and center point information corresponding to the target satellite are determined; Based on the residual error information, the scanning radius corresponding to the target satellite is determined; Based on the scanning radius and the center point information, the target scanning range corresponding to the target satellite is constructed.

4. The method according to claim 1, characterized in that, The aforementioned historical ephemeris information is a set of information from the first historical ephemeris information of the target satellite and the second historical ephemeris information of the laser emitting satellite corresponding to the target satellite. The step of determining multiple simulated relative positional relationships of the target satellite based on multiple historical ephemeris information includes: A preset coarse alignment model is retrieved, and the first historical ephemeris information and the second historical ephemeris information that have a corresponding relationship are substituted into the preset coarse alignment model to determine multiple simulated scanning ranges corresponding to the target satellite. Obtain the target position information of the target satellite corresponding to the plurality of historical ephemeris information respectively; Based on multiple simulated scanning ranges and multiple target location information, multiple simulated relative positional relationships corresponding to the target satellite are determined.

5. The method according to claim 1, characterized in that, The step of determining the scanning mode corresponding to the target scanning range using the multiple simulated relative positional relationships includes: Based on the multiple simulated relative positional relationships, multiple virtual two-dimensional planes corresponding to the target satellite are determined; The multiple virtual two-dimensional planes are overlapped based on time sequence to obtain a target virtual two-dimensional plane, wherein the target virtual two-dimensional plane contains multiple target location information corresponding to the target satellite; Determine the position change information corresponding to the multiple target position information; Based on the location change information, the scanning mode corresponding to the target scanning range is determined.

6. The method according to claim 5, characterized in that, Determining the scanning mode corresponding to the target scanning range based on the position change information includes: Based on a preset range division rule, the target scanning range is divided into regions to obtain multiple sub-target scanning ranges; Based on the position change information, the hit probability corresponding to the scanning range of the multiple sub-targets is determined; Based on the hit probability, the scanning order corresponding to the multiple target scanning ranges is determined, and based on the scanning order, the scanning mode corresponding to the target scanning range is determined.

7. The method according to claim 6, characterized in that, The target scanning range is divided into regions based on a preset range division rule to obtain multiple sub-target scanning ranges, including: Based on the multiple preset range division rules included in the preset range division rules, the target scanning range is divided to obtain an initial target scanning range, wherein the initial target scanning range includes a circular region and multiple annular regions; Based on the preset angle thresholds included in the preset range division rules, the initial target scanning range is divided to obtain the multiple sub-target scanning ranges.

8. A satellite-based laser communication connection device, characterized in that, include: The target scanning range determination module is used to retrieve coarse alignment assessment information corresponding to the target satellite when laser communication interruption information of the target satellite is obtained, and to determine the target scanning range corresponding to the target satellite based on the coarse alignment assessment information; The relative position relationship determination module is used to acquire historical ephemeris information corresponding to a preset number of historical unit time periods of the target satellite, and to determine multiple simulated relative position relationships of the target satellite based on the multiple historical ephemeris information. The laser communication reconnection module is used to determine the scanning mode corresponding to the target scanning range by utilizing the multiple simulated relative positional relationships, and to complete the laser scanning confirmation and interruption reconnection of the target satellite based on the scanning mode. The scanning mode is a mode for scanning the target scanning range based on a determined specific scanning rule.

9. An electronic device, characterized in that, include: processor; A memory storing a computer program that, when executed by the processor, causes the processor to perform the method as described in any one of claims 1-7.

10. A computer-readable medium having a computer program stored thereon, characterized in that, When the computer program is executed by a processor, the processor performs the method according to any one of claims 1-7.

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